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EH 2.0/10 (eh2010-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EH 2.0/10 (eh2010-il)
Reynolds number: 200,000
Max Cl/Cd: 62.99 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eh2010-il-200000-n5.txt
Download as CSV file: xf-eh2010-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EH 2.0/10                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5584   0.08638   0.08308  -0.0056   1.0000   0.0131
  -9.250  -0.5658   0.08065   0.07740  -0.0093   1.0000   0.0130
  -9.000  -0.5794   0.07373   0.07054  -0.0152   1.0000   0.0129
  -8.750  -0.5942   0.06820   0.06500  -0.0188   1.0000   0.0125
  -8.500  -0.6122   0.06200   0.05872  -0.0203   1.0000   0.0126
  -8.250  -0.6241   0.05545   0.05200  -0.0211   1.0000   0.0124
  -8.000  -0.6362   0.04751   0.04374  -0.0208   1.0000   0.0125
  -7.750  -0.6452   0.03963   0.03534  -0.0190   1.0000   0.0127
  -7.500  -0.6428   0.03420   0.02927  -0.0169   1.0000   0.0137
  -7.250  -0.6317   0.03079   0.02531  -0.0151   1.0000   0.0142
  -7.000  -0.6199   0.02733   0.02135  -0.0132   1.0000   0.0145
  -6.750  -0.6039   0.02472   0.01839  -0.0117   1.0000   0.0150
  -6.500  -0.5845   0.02306   0.01651  -0.0105   1.0000   0.0156
  -6.250  -0.5638   0.02172   0.01499  -0.0094   1.0000   0.0164
  -6.000  -0.5427   0.02045   0.01353  -0.0082   1.0000   0.0174
  -5.750  -0.5215   0.01925   0.01216  -0.0070   1.0000   0.0185
  -5.500  -0.4858   0.01810   0.01079  -0.0087   0.9783   0.0206
  -5.250  -0.4511   0.01694   0.00951  -0.0104   0.9516   0.0236
  -5.000  -0.4157   0.01613   0.00859  -0.0120   0.9226   0.0265
  -4.750  -0.3840   0.01548   0.00776  -0.0126   0.8913   0.0298
  -4.500  -0.3576   0.01482   0.00702  -0.0122   0.8602   0.0344
  -4.250  -0.3326   0.01437   0.00642  -0.0113   0.8315   0.0388
  -4.000  -0.3088   0.01393   0.00584  -0.0103   0.8055   0.0450
  -3.750  -0.2846   0.01360   0.00537  -0.0094   0.7820   0.0528
  -3.500  -0.2606   0.01323   0.00493  -0.0085   0.7603   0.0626
  -3.250  -0.2361   0.01295   0.00457  -0.0077   0.7402   0.0754
  -3.000  -0.2112   0.01270   0.00426  -0.0070   0.7214   0.0927
  -2.750  -0.1865   0.01243   0.00396  -0.0064   0.7038   0.1143
  -2.500  -0.1618   0.01215   0.00370  -0.0058   0.6875   0.1442
  -2.250  -0.1374   0.01182   0.00345  -0.0051   0.6718   0.1886
  -2.000  -0.1138   0.01139   0.00321  -0.0045   0.6570   0.2582
  -1.750  -0.0952   0.01047   0.00293  -0.0030   0.6435   0.4402
  -1.250  -0.0571   0.00938   0.00305   0.0018   0.6179   0.8014
  -1.000  -0.0300   0.00945   0.00312   0.0027   0.6050   0.8534
  -0.750  -0.0013   0.00957   0.00316   0.0032   0.5925   0.8857
  -0.500   0.0301   0.00972   0.00321   0.0030   0.5801   0.9087
  -0.250   0.0628   0.00989   0.00326   0.0026   0.5680   0.9276
   0.000   0.1042   0.01012   0.00336   0.0003   0.5556   0.9442
   0.250   0.1452   0.01030   0.00341  -0.0021   0.5432   0.9560
   0.500   0.1820   0.01037   0.00335  -0.0039   0.5318   0.9595
   0.750   0.2149   0.01041   0.00330  -0.0051   0.5204   0.9637
   1.000   0.2445   0.01047   0.00327  -0.0055   0.5097   0.9690
   1.250   0.2795   0.01052   0.00323  -0.0071   0.4989   0.9718
   1.500   0.3129   0.01058   0.00321  -0.0084   0.4885   0.9754
   1.750   0.3445   0.01064   0.00322  -0.0093   0.4781   0.9798
   2.000   0.3768   0.01070   0.00323  -0.0104   0.4677   0.9835
   2.250   0.4106   0.01076   0.00323  -0.0118   0.4577   0.9867
   2.750   0.4755   0.01091   0.00333  -0.0141   0.4377   0.9941
   3.000   0.5089   0.01098   0.00337  -0.0155   0.4277   0.9974
   3.250   0.5398   0.01108   0.00346  -0.0164   0.4185   1.0000
   3.500   0.5626   0.01118   0.00356  -0.0155   0.4092   1.0000
   3.750   0.5854   0.01130   0.00368  -0.0147   0.4006   1.0000
   4.000   0.6079   0.01144   0.00380  -0.0138   0.3922   1.0000
   4.250   0.6308   0.01157   0.00396  -0.0129   0.3831   1.0000
   4.500   0.6535   0.01173   0.00415  -0.0121   0.3747   1.0000
   4.750   0.6761   0.01190   0.00433  -0.0112   0.3656   1.0000
   5.000   0.6990   0.01207   0.00455  -0.0103   0.3566   1.0000
   5.250   0.7216   0.01227   0.00476  -0.0094   0.3480   1.0000
   5.500   0.7444   0.01247   0.00502  -0.0085   0.3386   1.0000
   5.750   0.7672   0.01268   0.00528  -0.0077   0.3293   1.0000
   6.000   0.7899   0.01292   0.00555  -0.0068   0.3197   1.0000
   6.250   0.8125   0.01316   0.00584  -0.0060   0.3098   1.0000
   6.500   0.8354   0.01341   0.00616  -0.0051   0.2991   1.0000
   6.750   0.8580   0.01368   0.00648  -0.0043   0.2876   1.0000
   7.000   0.8800   0.01397   0.00684  -0.0034   0.2717   1.0000
   7.250   0.9014   0.01433   0.00718  -0.0024   0.2518   1.0000
   7.500   0.9225   0.01474   0.00757  -0.0015   0.2275   1.0000
   7.750   0.9425   0.01527   0.00803  -0.0005   0.1989   1.0000
   8.000   0.9613   0.01596   0.00859   0.0006   0.1629   1.0000
   8.250   0.9772   0.01698   0.00938   0.0019   0.1178   1.0000
   8.500   0.9902   0.01831   0.01046   0.0035   0.0701   1.0000
   8.750   1.0017   0.01978   0.01171   0.0052   0.0368   1.0000
   9.000   1.0145   0.02105   0.01293   0.0069   0.0239   1.0000
   9.250   1.0281   0.02218   0.01416   0.0084   0.0187   1.0000
   9.500   1.0399   0.02340   0.01549   0.0102   0.0153   1.0000
   9.750   1.0525   0.02445   0.01666   0.0117   0.0131   1.0000
  10.000   1.0601   0.02579   0.01812   0.0137   0.0116   1.0000
  10.250   1.0593   0.02746   0.01991   0.0165   0.0109   1.0000
  10.500   1.0608   0.02886   0.02144   0.0189   0.0105   1.0000
  10.750   1.0605   0.03059   0.02332   0.0207   0.0100   1.0000
  11.000   1.0592   0.03272   0.02559   0.0218   0.0095   1.0000
  11.250   1.0579   0.03512   0.02816   0.0222   0.0092   1.0000
  11.500   1.0569   0.03773   0.03089   0.0223   0.0089   1.0000
  11.750   1.0560   0.04049   0.03377   0.0220   0.0087   1.0000
  12.000   1.0542   0.04348   0.03687   0.0217   0.0085   1.0000
  12.250   1.0530   0.04648   0.03998   0.0212   0.0083   1.0000
  12.500   1.0518   0.04956   0.04317   0.0206   0.0081   1.0000
  12.750   1.0496   0.05282   0.04653   0.0199   0.0079   1.0000
  13.000   1.0478   0.05609   0.04991   0.0192   0.0078   1.0000
  13.250   1.0452   0.05954   0.05346   0.0182   0.0076   1.0000
  13.500   1.0426   0.06305   0.05708   0.0173   0.0075   1.0000
  13.750   1.0408   0.06652   0.06068   0.0163   0.0075   1.0000
  14.000   1.0352   0.07059   0.06485   0.0150   0.0072   1.0000
  14.250   1.0312   0.07461   0.06900   0.0137   0.0072   1.0000
  14.500   1.0230   0.07949   0.07401   0.0117   0.0069   1.0000
  14.750   1.0177   0.08414   0.07883   0.0096   0.0068   1.0000
  15.000   1.0108   0.08925   0.08411   0.0071   0.0068   1.0000
  15.250   1.0040   0.09468   0.08972   0.0039   0.0065   1.0000
  15.500   0.9947   0.10053   0.09572   0.0011   0.0065   1.0000
  15.750   0.9851   0.10672   0.10206  -0.0022   0.0065   1.0000
  16.000   0.9745   0.11351   0.10903  -0.0062   0.0062   1.0000
  16.250   0.9630   0.12054   0.11621  -0.0100   0.0063   1.0000
  16.500   0.9512   0.12785   0.12366  -0.0141   0.0064   1.0000
  16.750   0.9380   0.13600   0.13196  -0.0189   0.0063   1.0000
  17.000   0.9250   0.14430   0.14037  -0.0235   0.0065   1.0000
  17.250   0.9106   0.15337   0.14956  -0.0286   0.0066   1.0000
  17.500   0.8963   0.16277   0.15903  -0.0337   0.0069   1.0000
  17.750   0.8813   0.17324   0.16957  -0.0393   0.0070   1.0000
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